Similarly shaped airfoils to GA 37-311
New! Bulk download of polars in Excel format: GA%2037-311.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
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2. NACA64-411 a=0.5
3. NACA63-411 a=0.5
4. GA 35A311
5. NACA64-411 a=0.6
6. NACA63-411 a=0.6
7. GA 40-311
8. GA 40A311
9. GA 37A311
10. NACA64-411 a=0.2
11. MS2.5/11GPV
12. NACA63-411 a=0.2
13. GA 35A310
14. NACA65-411 a=0.5
15. NACA64-411 a=0.8
16. HN-203
17. NACA63-411 a=0.8
18. GA 37A310
19. NACA65-411 a=0.6
20. GA 37-310
21. GA 37-312